ASTM F2799 - 14 (2019)

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Designation: F2799 −14 (Reapproved 2019)
Standard Practice for
Maintenance of Aircraft Electrical Wiring Systems
1
This standard is issued under the ﬁxed designation F2799; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope
1.1 Deﬁnition—This practice deﬁnes acceptable practices
and processes for the maintenance, preventative maintenance,
and repair of electric systems in general aviation aircraft. This
practice does not change or create any additional regulatory
requirements nor does it authorize changes in or permit
deviations from existing regulatory requirements.
1.2 Applicability—The guidance provided in this practice is
directed to air carriers, air operators, maintenance providers,
repair stations, and anyone performing maintenance or repairs.
1.3 Protections and Warnings—This practice provides guid-
ance to minimize contamination and accidental damage to
electrical wiring interconnection systems (EWIS) while work-
ing on aircraft.
1.4 “Protect and Clean As You Go” Philosophy—This
philosophy is applied to aircraft wiring through inclusion in
operators’ maintenance and training programs. This philosophy
stresses the importance of protective measures when working
on or around wire bundles and connectors. It stresses how
important it is to protect EWIS during structural repairs, (STC)
installations, or other alterations by ensuring that metal
shavings, debris, and contamination resulting from such work
are removed.
1.5 Units—The values stated in inch-pound units are to be
regarded as standard. The values given in parentheses are
mathematical conversions to SI units that are provided for
information only and are not considered standard.
NOTE 1—When SI units are required, refer to Annex 5 of ICAO.
1.6 This standard does not purport to address all of the
safety concerns, if any, associated with its use. It is the
responsibility of the user of this standard to establish appro-
priate safety, health, and environmental practices and deter-
mine the applicability of regulatory limitations prior to use.
1.7 This international standard was developed in accor-
dance with internationally recognized principles on standard-
ization established in the Decision on Principles for the
Development of International Standards, Guides and Recom-
mendations issued by the World Trade Organization Technical
Barriers to Trade (TBT) Committee.
2. Referenced Documents
2.1 ASTM Standards:
2
F2490 Guide for Aircraft Electrical Load and Power Source
Capacity Analysis
F2639 Practice for Design, Alteration, and Certiﬁcation of
Aircraft Electrical Wiring Systems
2.2 ICAO Standard:
3
ICAO Annex 5 Units of Measurement to Be Used in Air and
Ground Operations
2.3 JEDEC Standard:
4
EIA 471 Symbol and Label for Electrostatic Sensitive De-
vices
2.4 NEMA Standard:
5
WC 27500 Standards for Aerospace and Industrial Electric
Cable
2.5 RTCA Standard:
6
DO-160C Environmental Conditions and Test Procedures
for Airborne Equipment
2.6 SAE Standards:
7
AS4372 Performance Requirements for Wire, Electric, Insu-
lated Copper or Copper Alloy
AS4373 Test Methods for Insulated Electric Wire
AS21919 Clamp, Loop Type, Cushioned Support
AS22759 Wire, Electrical, Fluoropolymer-Insulated, Copper
or Copper Alloy
AS50881 Wiring Aerospace Vehicle
1
This practice is under the jurisdiction of ASTM Committee F39 on Aircraft
Systems and is the direct responsibility of Subcommittee F39.02 on Inspection,
Alteration, Maintenance, and Repair.
Current edition approved June 1, 2019. Published June 2019. Originally
approved in 2009. Last previous edition approved in 2014 as F2799–14. DOI:
10.1520/F2799–14R19.
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
Standards volume information, refer to the standard’s Document Summary page on
the ASTM website.
3
Available from International Civil Aviation Organization (ICAO), Customer
Services Unit, 999 Robert-Bourassa Boulevard, Montréal, Québec, H3C 5H7,
Canada, https://www.icao.int.
4
Available from the JEDEC Solid State Technology Association, 3103 N. 10th
St., Suite 240-S, Arlington, VA 22201-2107, https://www.jedec.org/.
5
Available from National Electrical Manufacturers Association (NEMA), 1300
N. 17th St., Suite 900, Arlington, VA 22209, http://www.nema.org.
6
Available from RTCA, Inc., 1150 18th NW, Suite 910, Washington, DC 20036,
https://www.rtca.org.
7
Available from Society of Automotive Engineers (SAE), 400 Commonwealth
Dr., Warrendale, PA 15096, https://www.sae.org.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the
Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
1
 

ARP1870 Aerospace Systems Electrical Bonding and

Grounding for Electromagnetic Compatibility and Safety

ARP1928 Torque Recommendations for Attaching Electrical

Wiring Devices to Terminal Boards or Blocks, Studs,

Posts, etc.

2.7 Federal Standards:

Advisory Circular 20-53A Protection of Aircraft Fuel Sys-

tems against Fuel Vapor Ignition due to Lightning

MIL-C-22520/2C Crimping Tools, Terminal, Hand, Wire

Termination

MIL-S-8802 Sealing Compound, Temperature-Resistant, In-

tegral Fuel Tanks and Fuel Cell Cavities, High Adhesion

MIL-T-7928 Terminal, Lug Splices, Conductors, Crimp

Style, Copper

MIL-T-43435 Tape, Lacing and Tying

MS17821 Speciﬁcation for Cable and Marker Color Code

Numbers

MS17822 Speciﬁcation for Cable and Marker Color Code

Numbers

NAVAIR 01-1A-505 Installation Practices—Aircraft Elec-

tric and Electronic Wiring

3. Terminology

3.1 Deﬁnitions:

3.1.1 maintenance, n—inspection, overhaul, repair,

preservation, and the replacement of parts but excludes pre-

ventive maintenance.

3.2 Deﬁnitions of Terms Speciﬁc to This Standard:

3.2.1 electrical wiring interconnection system (EWIS),

n—as used in this practice, any wire, wiring device, or

combination of these, including termination devices, installed

in any area of the aircraft for the purpose of transmitting

electrical energy between two or more intended termination

points.

3.3 Acronyms:

3.3.1 AC—alternating current

3.3.2 CFC—carbon ﬁber composite

3.3.3 DC—direct current

3.3.4 EDS—electronic data system

3.3.5 EMI—electromagnetic interference

3.3.6 ESD—electrostatic discharge

3.3.7 EWIS—electrical wiring interconnection system

3.3.8 ICAO—International Civil Aviation Organization

3.3.9 NiCad—nickel cadmium

3.3.10 OEM—original equipment manufacturer

3.3.11 PC—personal computer

3.3.12 PTFE—polytetraﬂuoroethylene

3.3.13 RF—radio frequency

3.3.14 SOC—state of charge

3.3.15 STC—supplemental-type certiﬁcate

3.3.16 SWAMP—severe wind and moisture problem

3.3.17 UV—ultraviolet

4. Signiﬁcance and Use

4.1 This practice is intended to be used as a standard wiring

practice for aircraft when not contrary to standards published

by the aircraft original equipment manufacturer (OEM) or

regulations. This practice is intended to be used for mainte-

nance and preventive maintenance of electrical wiring inter-

connection systems (EWIS).

4.2 This practice is not intended to supersede or replace any

government speciﬁcation or speciﬁc manufacturer’s instruc-

tions regarding EWIS maintenance or repair.

5. Maintenance

5.1 Electrical Systems:

5.1.1 Maintenance:

5.1.1.1 Scheduled and unscheduled maintenance activities,

if done improperly, may contribute to long-term problems and

degradation of wiring. Certain repairs may have limited dura-

bility and shall be evaluated to ascertain if rework is necessary.

Repairs that conform to manufacturers’ recommended mainte-

nance practices are generally considered permanent and should

not require rework. Care shall be taken to prevent undue

collateral damage to EWIS while performing maintenance on

other systems. Metal shavings and debris have been discovered

on wire bundles after maintenance, repairs, or modiﬁcations

have been performed. Care shall be taken to protect wire

bundles and connectors during maintenance and repair. Work

areas should be cleaned while the work progresses to ensure

that all shavings and debris are removed. The work area should

be thoroughly cleaned after work is complete, and the area

shall be inspected after the ﬁnal cleaning. Maintenance,

repairs, and alterations should be performed using the most

effective methods available to protect the surrounding EWIS.

Since wire splices are more susceptible to degradation, arcing,

and overheating, the recommended method of repairing a wire

is with an environmentally sealed splice. (Warning—For

personal safety and to avoid the possibility of ﬁre, turn off all

electrical power before starting an inspection of the aircraft

electrical system or performing maintenance.)

5.1.1.2 Repair of any system component that fails an elec-

trical measurement test shall conform to manufacturer’s in-

structions and, in lieu of manufacturer’s manuals, Practice

F2639 or appropriate regulatory guidance materials.

5.1.1.3 Wire bundles should be routed in accessible areas

that are protected from damage from personnel, cargo, and

maintenance activity. They should not be routed in areas where

they are likely to be used as handholds or as support for

personal equipment or where they could become damaged

during removal of aircraft equipment.

5.1.1.4 Replacement wires (see Tables 1 and 2) should be

clamped so that contact with equipment and structure is

avoided. Where this cannot be accomplished, extra protection

in the form of grommets, chafe strips, and so forth, should be

provided. Protective grommets shall be used wherever wires

cannot be clamped in a way that ensures at least a

⁄

in. (9.5

mm) clearance from structure at penetrations.

Available from U.S. Government Publishing Office, 732 N. Capitol St., NW,

Washington, DC 20401, http://www.gpo.gov.

F2799 − 14 (2019)

5.1.1.5 Wire should not have a preload against the corners

or edges of chaﬁng strips or grommets. Wiring shall be routed

away from high-temperature equipment and lines to prevent

deterioration of insulation. Protective ﬂexible conduits should

be made of a material and design that eliminates the potential

of chaﬁng between their internal wiring and the conduit

internal walls.

5.1.1.6 Replacement wires that shall be routed across

hinged panels should be routed and clamped so that the bundle

will twist, rather than bend, when the panel is moved.

5.1.2 General:

5.1.2.1 The term “electrical wiring interconnection system

(EWIS)” as used in this practice means any wire, wiring

device, or combination of these, including termination devices,

installed in any area of the aircraft for the purpose of

transmitting electrical energy between two or more intended

termination points.

5.1.2.2 The satisfactory performance of an aircraft is depen-

dent upon the continued reliability of the electrical system.

Damaged wiring or equipment in an aircraft, regardless of how

minor it may appear to be, cannot be tolerated. Reliability of

the system is proportional to the amount of maintenance

TABLE 1 Open Wiring

Document Voltage Rating

(Maximum)

Rated Wire

Temperature, °C Insulation Type Conductor Type

MIL-W-22759/1

600 200 Fluoropolymer-insulated TFE and TFE coated glass Silver-coated copper

MIL-W-22759/2

600 260 Fluoropolymer-insulated TFE and TFE coated glass Nickel-coated copper

MIL-W-22759/3

600 260 Fluoropolymer-insulated TFE-glass-TFE Nickel-coated copper

MIL-W-22759/4

600 200 Fluoropolymer-insulated TFE-glass-FEP Silver-coated copper

MIL-W-22759/5

600 200 Fluoropolymer-insulated extruded TFE Silver-coated copper

MIL-W-22759/6

600 260 Fluoropolymer-insulated extruded TFE Nickel-coated copper

MIL-W-22759/7

600 200 Fluoropolymer-insulated extruded TFE Silver-coated copper

MIL-W-22759/8

600 260 Fluoropolymer-insulated extruded TFE Nickel-coated copper

MIL-W-22759/9

1000 200 Fluoropolymer-insulated extruded TFE Silver-coated copper

MIL-W-22759/10

1000 260 Fluoropolymer-insulated Nickel-coated copper

MIL-W-22759/13

600 135 Fluoropolymer-insulated FEP PVF2 Tin-coated copper,

MIL-W-22759/16

600 150 Fluoropolymer-insulated extruded ETFE Tin-coated copper,

MIL-W-22759/17

600 150 Fluoropolymer-insulated extruded ETFE Silver-coated high-strength copper alloy

MIL-W-22759/20

1000 200 Fluoropolymer-insulated extruded TFE Silver-coated high-strength copper alloy

MIL-W-22759/21

1000 260 Fluoropolymer-insulated extruded TFE Nickel-coated high-strength copper alloy

MIL-W-22759/34

600 150 Fluoropolymer-insulated cross-linked modiﬁed ETFE Tin-coated copper

MIL-W-22759/35

600 200 Fluoropolymer-insulated cross-linked modiﬁed ETFE Silver-coated high-strength copper alloy

MIL-W-22759/41

600 200 Fluoropolymer-insulated cross-linked modiﬁed ETFE Nickel-coated copper

MIL-W-22759/42

600 200 Fluoropolymer-insulated cross-linked modiﬁed ETFE Nickel-coated high-strength copper alloy

MIL-W-22759/43

600 200 Fluoropolymer-insulated cross-linked modiﬁed ETFE Silver-coated copper

MIL-W-25038/3/2/ 600 260 See speciﬁcation sheet

See speciﬁcation sheet

MIL-W-81044/6 600 150 Cross-linked polyalkene Tin-coated copper

MIL-W-81044/7 600 150 Cross-linked polyalkene Silver-coated high-strength copper alloy

MIL-W-81044/9 600 150 Cross-linked polyalkene Tin-coated copper

MIL-W-81044/10 600 150 Cross-linked polyalkene Silver-coated high-strength copper alloy

MIL-W-81044/12 600 150 Cross-linked polyalkene Tin-coated copper

MIL-W-22759 has been replaced by SAE AS22759.

Inorganic ﬁbers—glass—TFE.

TABLE 2 Protected Wiring

Document Voltage Rating

(Maximum)

Rated Wire

Temperature, °C Insulation Type Conductor Type

MIL-W-22759/11

600 200 Fluoropolymer-insulated extruded TFE Silver-coated copper

MIL-W-22759/12

600 260 Fluoropolymer-insulated extruded TFE Nickel-coated copper

MIL-W-22759/14

600 135 Fluoropolymer-insulated FEP-PVF2 Tin-coated copper

MIL-W-22759/15

600 135 Fluoropolymer-insulated FEP-PVF2 Silver-plated high-strength copper alloy

MIL-W-22759/18

600 150 Fluoropolymer-insulated extruded ETFE Tin-coated copper

MIL-W-22759/19

600 150 Fluoropolymer-insulated extruded ETFE Silver-coated high-strength copper alloy

MIL-W-22759/22

600 200 Fluoropolymer-insulated extruded TFE Silver-coated high-strength copper alloy

MIL-W-22759/23

600 260 Fluoropolymer-insulated extruded TFE Nickel-coated high-strength copper alloy

MIL-W-22759/32

600 150 Fluoropolymer-insulated cross-linked modiﬁed ETFE Tin-coated copper

MIL-W-22759/33

600 200 Fluoropolymer-insulated cross-linked modiﬁed ETFE Silver-coated high-strength copper alloy

MIL-W-22759/44

600 200 Fluoropolymer-insulated cross-linked modiﬁed ETFE Silver-coated copper

MIL-W-22759/45

600 200 Fluoropolymer-insulated cross-linked modiﬁed ETFE Nickel-coated copper

MIL-W-22759/46

600 200 Fluoropolymer-insulated cross-linked modiﬁed ETFE Nickel-coated high-strength copper alloy

MIL-W-81044/13 600 150 Cross-linked polyalkene – PVF2 Silver-coated high-strength copper alloy

MIL-W-81381/17 600 200 Fluorocarbon polyamide Silver-coated copper

MIL-W-81381/18 600 200 Fluorocarbon polyamide Nickel-coated copper

MIL-W-81381/19 600 200 Fluorocarbon polyamide Silver-coated high-strength copper alloy

MIL-W-81381/20 600 200 Fluorocarbon polyamide Nickel-coated high-strength copper alloy

MIL-W-81381/21 600 150 Fluorocarbon polyamide Tin-coated copper

MIL-W-22759 has been replaced by SAE AS22759.

F2799 − 14 (2019)

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摘要：

该标准规范 ASTMF2799 – 14 (2019) 由美国材料与试验协会发布，主要针对金属材料在增材制造（即3D打印）过程中的拉伸试样标准与测试方法进行了详细规定。该文档为2014年首次发布、2019年复审确认的最新版本，确保制造商、实验室和研究机构能够统一采用标准化的试样几何形状、构建方向以及测试条件，从而获得可比性高的力学性能数据。内容涵盖试验机的校准要求、数据处理方法以及报告格式，适用于激光粉末床熔融、电子束熔融等多种金属增材制造工艺。遵循该标准有助于提升产品质量控制水平，减少批次间差

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